EP3034834A1 - Method for managing power demand for the operation of an unmanned aircraft provided with an internal combustion engine - Google Patents
Method for managing power demand for the operation of an unmanned aircraft provided with an internal combustion engine Download PDFInfo
- Publication number
- EP3034834A1 EP3034834A1 EP14307051.4A EP14307051A EP3034834A1 EP 3034834 A1 EP3034834 A1 EP 3034834A1 EP 14307051 A EP14307051 A EP 14307051A EP 3034834 A1 EP3034834 A1 EP 3034834A1
- Authority
- EP
- European Patent Office
- Prior art keywords
- aircraft
- internal combustion
- combustion engine
- power
- electrical energy
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B65/00—Adaptations of engines for special uses not provided for in groups F02B61/00 or F02B63/00; Combinations of engines with other devices, e.g. with non-driven apparatus
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B64C27/04—Helicopters
- B64C27/12—Rotor drives
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B60K—ARRANGEMENT OR MOUNTING OF PROPULSION UNITS OR OF TRANSMISSIONS IN VEHICLES; ARRANGEMENT OR MOUNTING OF PLURAL DIVERSE PRIME-MOVERS IN VEHICLES; AUXILIARY DRIVES FOR VEHICLES; INSTRUMENTATION OR DASHBOARDS FOR VEHICLES; ARRANGEMENTS IN CONNECTION WITH COOLING, AIR INTAKE, GAS EXHAUST OR FUEL SUPPLY OF PROPULSION UNITS IN VEHICLES
- B60K6/00—Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines ; Control systems therefor, i.e. systems controlling two or more prime movers, or controlling one of these prime movers and any of the transmission, drive or drive units Informative references: mechanical gearings with secondary electric drive F16H3/72; arrangements for handling mechanical energy structurally associated with the dynamo-electric machine H02K7/00; machines comprising structurally interrelated motor and generator parts H02K51/00; dynamo-electric machines not otherwise provided for in H02K see H02K99/00
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- B60K6/22—Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines ; Control systems therefor, i.e. systems controlling two or more prime movers, or controlling one of these prime movers and any of the transmission, drive or drive units Informative references: mechanical gearings with secondary electric drive F16H3/72; arrangements for handling mechanical energy structurally associated with the dynamo-electric machine H02K7/00; machines comprising structurally interrelated motor and generator parts H02K51/00; dynamo-electric machines not otherwise provided for in H02K see H02K99/00 the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs characterised by apparatus, components or means specially adapted for HEVs
- B60K6/24—Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines ; Control systems therefor, i.e. systems controlling two or more prime movers, or controlling one of these prime movers and any of the transmission, drive or drive units Informative references: mechanical gearings with secondary electric drive F16H3/72; arrangements for handling mechanical energy structurally associated with the dynamo-electric machine H02K7/00; machines comprising structurally interrelated motor and generator parts H02K51/00; dynamo-electric machines not otherwise provided for in H02K see H02K99/00 the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs characterised by apparatus, components or means specially adapted for HEVs characterised by the combustion engines
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- B60K6/38—Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines ; Control systems therefor, i.e. systems controlling two or more prime movers, or controlling one of these prime movers and any of the transmission, drive or drive units Informative references: mechanical gearings with secondary electric drive F16H3/72; arrangements for handling mechanical energy structurally associated with the dynamo-electric machine H02K7/00; machines comprising structurally interrelated motor and generator parts H02K51/00; dynamo-electric machines not otherwise provided for in H02K see H02K99/00 the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs characterised by apparatus, components or means specially adapted for HEVs characterised by the driveline clutches
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- B60K6/00—Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines ; Control systems therefor, i.e. systems controlling two or more prime movers, or controlling one of these prime movers and any of the transmission, drive or drive units Informative references: mechanical gearings with secondary electric drive F16H3/72; arrangements for handling mechanical energy structurally associated with the dynamo-electric machine H02K7/00; machines comprising structurally interrelated motor and generator parts H02K51/00; dynamo-electric machines not otherwise provided for in H02K see H02K99/00
- B60K6/20—Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines ; Control systems therefor, i.e. systems controlling two or more prime movers, or controlling one of these prime movers and any of the transmission, drive or drive units Informative references: mechanical gearings with secondary electric drive F16H3/72; arrangements for handling mechanical energy structurally associated with the dynamo-electric machine H02K7/00; machines comprising structurally interrelated motor and generator parts H02K51/00; dynamo-electric machines not otherwise provided for in H02K see H02K99/00 the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs
- B60K6/22—Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines ; Control systems therefor, i.e. systems controlling two or more prime movers, or controlling one of these prime movers and any of the transmission, drive or drive units Informative references: mechanical gearings with secondary electric drive F16H3/72; arrangements for handling mechanical energy structurally associated with the dynamo-electric machine H02K7/00; machines comprising structurally interrelated motor and generator parts H02K51/00; dynamo-electric machines not otherwise provided for in H02K see H02K99/00 the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs characterised by apparatus, components or means specially adapted for HEVs
- B60K6/40—Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines ; Control systems therefor, i.e. systems controlling two or more prime movers, or controlling one of these prime movers and any of the transmission, drive or drive units Informative references: mechanical gearings with secondary electric drive F16H3/72; arrangements for handling mechanical energy structurally associated with the dynamo-electric machine H02K7/00; machines comprising structurally interrelated motor and generator parts H02K51/00; dynamo-electric machines not otherwise provided for in H02K see H02K99/00 the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs characterised by apparatus, components or means specially adapted for HEVs characterised by the assembly or relative disposition of components
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B60—VEHICLES IN GENERAL
- B60K—ARRANGEMENT OR MOUNTING OF PROPULSION UNITS OR OF TRANSMISSIONS IN VEHICLES; ARRANGEMENT OR MOUNTING OF PLURAL DIVERSE PRIME-MOVERS IN VEHICLES; AUXILIARY DRIVES FOR VEHICLES; INSTRUMENTATION OR DASHBOARDS FOR VEHICLES; ARRANGEMENTS IN CONNECTION WITH COOLING, AIR INTAKE, GAS EXHAUST OR FUEL SUPPLY OF PROPULSION UNITS IN VEHICLES
- B60K6/00—Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines ; Control systems therefor, i.e. systems controlling two or more prime movers, or controlling one of these prime movers and any of the transmission, drive or drive units Informative references: mechanical gearings with secondary electric drive F16H3/72; arrangements for handling mechanical energy structurally associated with the dynamo-electric machine H02K7/00; machines comprising structurally interrelated motor and generator parts H02K51/00; dynamo-electric machines not otherwise provided for in H02K see H02K99/00
- B60K6/20—Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines ; Control systems therefor, i.e. systems controlling two or more prime movers, or controlling one of these prime movers and any of the transmission, drive or drive units Informative references: mechanical gearings with secondary electric drive F16H3/72; arrangements for handling mechanical energy structurally associated with the dynamo-electric machine H02K7/00; machines comprising structurally interrelated motor and generator parts H02K51/00; dynamo-electric machines not otherwise provided for in H02K see H02K99/00 the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs
- B60K6/42—Arrangement or mounting of plural diverse prime-movers for mutual or common propulsion, e.g. hybrid propulsion systems comprising electric motors and internal combustion engines ; Control systems therefor, i.e. systems controlling two or more prime movers, or controlling one of these prime movers and any of the transmission, drive or drive units Informative references: mechanical gearings with secondary electric drive F16H3/72; arrangements for handling mechanical energy structurally associated with the dynamo-electric machine H02K7/00; machines comprising structurally interrelated motor and generator parts H02K51/00; dynamo-electric machines not otherwise provided for in H02K see H02K99/00 the prime-movers consisting of electric motors and internal combustion engines, e.g. HEVs characterised by the architecture of the hybrid electric vehicle
- B60K6/44—Series-parallel type
- B60K6/442—Series-parallel switching type
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- B64C39/02—Aircraft not otherwise provided for characterised by special use
- B64C39/024—Aircraft not otherwise provided for characterised by special use of the remote controlled vehicle type, i.e. RPV
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/026—Aircraft characterised by the type or position of power plants comprising different types of power plants, e.g. combination of a piston engine and a gas-turbine
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- B—PERFORMING OPERATIONS; TRANSPORTING
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- B64U50/12—Propulsion using turbine engines, e.g. turbojets or turbofans
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
- F02B33/00—Engines characterised by provision of pumps for charging or scavenging
- F02B33/32—Engines with pumps other than of reciprocating-piston type
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
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- F02C6/14—Gas-turbine plants having means for storing energy, e.g. for meeting peak loads
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
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- F05D2220/60—Application making use of surplus or waste energy
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- F05D2220/70—Application in combination with
- F05D2220/76—Application in combination with an electrical generator
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
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- Y02T10/12—Improving ICE efficiencies
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T10/00—Road transport of goods or passengers
- Y02T10/60—Other road transportation technologies with climate change mitigation effect
- Y02T10/62—Hybrid vehicles
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the present invention relates to a method of managing a power demand for the operation of a rotary wing type unmanned aircraft equipped with an internal combustion engine.
- Devices having a rotary wing comprising a single power unit to ensure the training of at least one rotor of the wing.
- Such a power unit is then sized to provide the power necessary for the device to ensure its propulsion and / or lift.
- this power unit It is sometimes necessary for this power unit to be an internal combustion engine of the DIESEL engine type for applications where certain fuels such as gasoline can not be used.
- the DIESEL engine offer for the aeronautical market is very limited, which sometimes involves aircraft engines - with high reliability - but whose power is not always adapted to the aircraft and / or the density of the aircraft. power is usually limited.
- turbocharger to the existing engine is a solution generally used to achieve additional power input to the motor shaft.
- This turbocharger makes it possible to ensure a supercharging of air at the inlet of the pistons, thus substantially increasing the power developed by the engine.
- the modification of the injection laws is also a way to increase the power of the engine.
- auxiliary power unit auxiliary power unit
- Such auxiliary power units are generally used to power auxiliary circuits such as hydraulic or pneumatic, and are never used to drive a power transmission of at least one rotor on a rotary wing aircraft.
- the present invention aims at overcoming the various disadvantages set out above by proposing a method of managing a power demand to ensure the operation of a rotary wing aircraft of the drone type, which is particularly simple in its design and in its operating mode. reliable and economical, and able to take into account dynamically variations in the maximum power provided by the main motor of this device.
- Another object of the present invention is such a method ensuring recovery of the apparatus in the event of failure of its main power unit, the apparatus being devoid of redundancy.
- Yet another object of the invention is a rotary wing aircraft such as a vertical take-off drone (VTOL), whose original arrangement of its propulsion chain authorizes the implementation of this method of managing a request for control. power.
- VTOL vertical take-off drone
- the invention relates to a method, said aircraft comprising an internal combustion engine providing a maximum main power P M likely to vary.
- This management method thus provides a global method for managing the power required for the operation of an unmanned aircraft, in particular a rotary wing drone.
- This method of managing a power demand is particularly advantageous in the event that it is desired to increase the installed power of a vertical take-off drone.
- the addition of the mass related to the implementation of new equipment / systems is offset by an overall efficiency gain in the propulsion chain and a possibility of recovery of the drone in the event of engine damage.
- the increase in installed capacity allows either to transport more fuel to increase the autonomy of the drone, or to carry more payload, more securely.
- the turbine used in step b) is an additional turbine that is not part of, or not connected to, the internal combustion engine.
- This additional turbine is advantageously placed downstream of the turbine of the turbocharger.
- Said at least one energy storage unit is selected from the group consisting of an electric battery, a supercapacitor, ...
- the present invention also relates to a rotary-wing unmanned aircraft for the implementation of the power demand management method as described above, said aircraft comprising a supercharged internal combustion engine for moving said rotary wing, said internal combustion engine having a first compressor and providing a maximum main power to ensure at least the training of said rotary wing, said maximum main power being likely to vary.
- This supercharged internal combustion engine developing a maximum main power P M is connected to a main gearbox to rotate it so as to rotate at least one rotor of the rotary wing.
- This internal combustion engine is preferably a diesel engine.
- said internal combustion engine comprises a second compressor configured to be supplied with electrical energy by said at least one of said electrical energy storage units.
- This second compressor is an electric compressor.
- this aircraft comprises an electric motor configured to be supplied with electrical energy by said or at least one of said electrical energy storage units, said electric motor being connected to the main gearbox to which said engine is connected. internal combustion.
- this rotary wing aircraft comprising at least two rotors, it comprises a means for disengaging the mechanical coupling of said rotors so as to ensure a free rotation of these rotors when said internal combustion engine is out of order.
- this aircraft comprises a system for managing the state of charge of each electrical energy storage unit in order to continuously dispose of a recovery energy of the aircraft in the event of failure of said internal combustion engine.
- the figure 1 is a schematic view of the decision tree implemented by appropriate software in the propulsion control unit (PCU) for managing a power demand for the operation of a VTOL drone, according to an embodiment particular of the present invention.
- PCU propulsion control unit
- This drone comprises a power storage unit whose power supply and the return on the motor shaft of this electrical energy are managed by the propulsion control unit (PCU).
- PCU propulsion control unit
- This strategy for managing a power call is here described in the form of a decision tree composed of five (5) tests and six (6) modes of operation.
- a first test evaluates, by means of different sensors placed on the internal combustion engine, the operating state of the latter. If these sensors address signals indicating a failure thereof, a security mode (MODE F) is engaged to ensure a supply of electrical power directly from the energy storage unit to allow an autorotation assisted and a soft landing of the drone.
- MODE F security mode
- This mode is temporary and does not require an emergency landing.
- the electric motor / alternator 10 operating at high speed is capable of supplying or recovering the mechanical power on the turbocharger shaft of the diesel engine 12.
- the electric motor / alternator 11 connected to the mechanical transmission between the engine block 12 and the main rotor 13 makes it possible to supply mechanical power to the rotors of the VTOL drone.
- the two AC / DC converters 14, 15 make it possible to convert the electric power carried by direct current into electrical power carried by alternating current and vice versa.
- the DC / DC converter 16 regulates the current supplying the energy storage unit during charging.
- the energy storage unit 17 makes it possible to store or restore the electrical power to / from the electric motors / alternators.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Transportation (AREA)
- Chemical Kinetics & Catalysis (AREA)
- General Chemical & Material Sciences (AREA)
- Engine Equipment That Uses Special Cycles (AREA)
- Hybrid Electric Vehicles (AREA)
- Supercharger (AREA)
- Electric Propulsion And Braking For Vehicles (AREA)
- Charge And Discharge Circuits For Batteries Or The Like (AREA)
Abstract
Procédé de gestion d'une demande de puissance P D pour assurer le fonctionnement d'un aéronef sans pilote, cet aéronef comportant un moteur à combustion interne (12) fournissant une puissance principale maximale P M susceptible de varier, dans lequel une tubine est alimentée avec les gaz d'échappement et entraîne un générateur électrique, l'énergie électrique étant ou bien stockée ou bien utilisée pour assister le moteur à combustion interne. Ce procédé de gestion est particulièrement adapté à un aéronef sans pilote à voilure tournante, en permettant le stockage d'une énergie électrique au moins égale à une énergie de récupération de l'aéronef en cas de panne du moteur à combustion interne, cette énergie de récupération permettant le contrôle de l'autorotation de l'aéronef et son atterrissage.A method of managing a PD power demand to operate an unmanned aircraft, said aircraft having an internal combustion engine (12) providing a maximum main power PM that can vary, wherein a tubule is powered with the exhaust gas and drives an electric generator, the electrical energy being either stored or used to assist the internal combustion engine. This management method is particularly adapted to a rotary wing unmanned aircraft, by allowing the storage of electrical energy at least equal to a recovery energy of the aircraft in the event of failure of the internal combustion engine, this energy of recovery to control the autorotation of the aircraft and landing.
Description
La présente invention concerne un procédé de gestion d'une demande de puissance pour le fonctionnement d'un aéronef sans pilote de type à voilure tournante, équipé d'un moteur à combustion interne.The present invention relates to a method of managing a power demand for the operation of a rotary wing type unmanned aircraft equipped with an internal combustion engine.
Elle concerne encore un aéronef sans pilote à voilure tournante muni d'un turbomoteur pour la mise en oeuvre de ce procédé de gestion.It also relates to a rotary wing unmanned aircraft equipped with a turbine engine for the implementation of this management method.
On connaît des appareils munis d'une voilure tournante comprenant une unique unité motrice pour assurer l'entrainement d'au moins un rotor de la voilure.Devices are known having a rotary wing comprising a single power unit to ensure the training of at least one rotor of the wing.
Une telle unité motrice est alors dimensionnée pour fournir la puissance nécessaire à l'appareil afin d'assurer sa propulsion et/ou sa sustentation.Such a power unit is then sized to provide the power necessary for the device to ensure its propulsion and / or lift.
Il est parfois nécessaire que cette unité motrice soit un moteur à combustion interne du type moteur DIESEL pour des applications où certains carburants tels que de l'essence, ne peuvent être mis en oeuvre.It is sometimes necessary for this power unit to be an internal combustion engine of the DIESEL engine type for applications where certain fuels such as gasoline can not be used.
Or, l'offre moteur DIESEL pour le marché aéronautique est très restreinte, ce qui implique parfois d'avionner des moteurs automobiles - à grande fiabilité - mais dont la puissance n'est pas toujours adaptée à l'aéronef et/ou la densité de puissance est généralement limitée.However, the DIESEL engine offer for the aeronautical market is very limited, which sometimes involves aircraft engines - with high reliability - but whose power is not always adapted to the aircraft and / or the density of the aircraft. power is usually limited.
De plus, sur un drone à décollage vertical, la demande de puissance est souvent maximale sur les phases de décollage et les phases stationnaires, phases qui, sur de nombreuses missions, ont une durée relativement courtes.Moreover, on a vertical take-off UAV, the demand for power is often maximum on the take-off and stationary phases, phases which, on many missions, have a relatively short duration.
Il est donc souvent nécessaire de « booster » la puissance initiale du moteur pour parvenir à des performances installées acceptables.It is therefore often necessary to "boost" the initial power of the engine to achieve acceptable installed performance.
L'ajout d'un turbocompresseur au moteur existant est une solution généralement utilisée pour parvenir à un apport de puissance supplémentaire sur l'arbre moteur.The addition of a turbocharger to the existing engine is a solution generally used to achieve additional power input to the motor shaft.
Ce turbocompresseur permet d'assurer une suralimentation en air en entrée des pistons augmentant ainsi sensiblement la puissance développée par le moteur.This turbocharger makes it possible to ensure a supercharging of air at the inlet of the pistons, thus substantially increasing the power developed by the engine.
La modification des lois d'injections est également un moyen d'accroître la puissance du moteur.The modification of the injection laws is also a way to increase the power of the engine.
Dans ces deux cas, Il faut s'assurer que les paramètres limites du moteur (température en entrée de la turbine du turbocompresseur, pression de la culasse) ne soient pas impactés par ces modifications ou que ces dernières autorisent une durée de vie du moteur minimale.In both cases, it must be ensured that the limit parameters of the engine (turbocharger turbine inlet temperature, cylinder head pressure) are not affected by these modifications or that they allow a minimum engine life. .
Une telle solution peut également demander de plus lourdes modifications sur le refroidissement moteur, les joints d'étanchéité, ...Such a solution may also require heavier modifications on engine cooling, seals, etc.
Quoiqu'il en soit, on observe que ces solutions peuvent s'avérer insuffisantes pour assurer un fonctionnement optimal de l'appareil à voilure tournante, la puissance maximale développée par un moteur DIESEL étant variable et dépendante de l'altitude de cet appareil et des conditions de température.Be that as it may, it is observed that these solutions may be insufficient to ensure optimal operation of the rotary wing aircraft, the maximum power developed by a DIESEL engine being variable and dependent on the altitude of this aircraft and the temperature conditions.
Ces variations de puissance maximale disponible sont suffisamment importantes pour devoir être considérées et définir une stratégie dynamique.These variations of maximum available power are sufficiently important to be considered and define a dynamic strategy.
On connait, par ailleurs, la mise en oeuvre sur certains aéronefs d'unité motrice auxiliaire thermique, connue sous l'acronyme APU (« auxiliaire power unit).It is known, moreover, the implementation on some aircraft auxiliary power unit, known by the acronym APU ("auxiliary power unit).
De telles unités motrices auxiliaires sont généralement utilisées pour alimenter des circuits auxiliaires tels qu'hydraulique ou pneumatique, et ne servent jamais à entraîner une boîte de transmission de puissance d'au moins un rotor sur un aéronef à voilure tournante.Such auxiliary power units are generally used to power auxiliary circuits such as hydraulic or pneumatic, and are never used to drive a power transmission of at least one rotor on a rotary wing aircraft.
D'autre part, lorsque l'unique unité motrice de l'appareil à voilure tournante tombe en panne, cet appareil étant dépourvu d'éléments de sécurité redondants pour prendre la relève sans interruption de service, cet appareil s'écrase de manière non contrôlée.On the other hand, when the single power unit of the rotary wing aircraft fails, this aircraft being devoid of redundant security elements to take over without interruption of service, this aircraft crashes uncontrollably .
Il existe donc un besoin important pour garantir qu'un appareil à voilure tournante en opération puisse atterrir de manière sécurisé en cas de défaillance de son unité motrice.There is therefore an important need to ensure that a rotary wing aircraft in operation can land safely in the event of failure of its power unit.
La présente invention vise à pallier les divers inconvénients ci-dessus exposés en proposant un procédé de gestion d'un appel de puissance pour assurer le fonctionnement d'un appareil à voilure tournante de type drone, particulièrement simple dans sa conception et dans son mode opératoire, fiable et économique, et capable de prendre en compte de manière dynamique les variations dans la puissance maximale fournie par le moteur principal de cet appareil.The present invention aims at overcoming the various disadvantages set out above by proposing a method of managing a power demand to ensure the operation of a rotary wing aircraft of the drone type, which is particularly simple in its design and in its operating mode. reliable and economical, and able to take into account dynamically variations in the maximum power provided by the main motor of this device.
Un autre objet de la présente invention est un tel procédé assurant une récupération de l'appareil en cas de défaillance de son unité motrice principale, l'appareil étant dépourvu de redondance.Another object of the present invention is such a method ensuring recovery of the apparatus in the event of failure of its main power unit, the apparatus being devoid of redundancy.
Encore un objet de l'invention est un aéronef à voilure tournante tel qu'un drone à décollage vertical (VTOL), dont l'agencement original de sa chaîne de propulsion autorise la mise en oeuvre de ce procédé de gestion d'une demande de puissance.Yet another object of the invention is a rotary wing aircraft such as a vertical take-off drone (VTOL), whose original arrangement of its propulsion chain authorizes the implementation of this method of managing a request for control. power.
A cet effet, l'invention concerne un procédé, ledit aéronef comportant un moteur à combustion interne fournissant une puissance principale maximale PM susceptible de varier.For this purpose, the invention relates to a method, said aircraft comprising an internal combustion engine providing a maximum main power P M likely to vary.
Selon l'invention, on réalise les étapes suivantes, en l'absence de panne dudit moteur à combustion interne :
- a) collecter au moins une partie des gaz d'échappement lorsque ce moteur à combustion interne fonctionne,
- b) alimenter une turbine avec l'énergie des gaz ainsi collectés,
- c) produire un courant électrique à partir d'un générateur électrique relié à ladite turbine, et
- d) comparer la puissance principale maximale PM fournie par ledit moteur à combustion interne lors de la demande de puissance avec la puissance PD demandée,
- e) lorsque la puissance principale maximale PM est au moins égale à la puissance PD demandée, stocker au moins une partie de cette énergie électrique ainsi générée dans au moins une unité de stockage d'énergie et/ou utiliser au moins une partie de cette énergie électrique ainsi générée pour assister le moteur à combustion interne, en fournissant une puissance auxiliaire PA complétant une puissance principale Pt développée par le moteur à combustion interne, avec Pt inférieur à PM, de sorte que PA + Pt = PD, ou
- f) lorsque la puissance principale maximale PM est inférieure à la puissance PD demandée pour le fonctionnement dudit aéronef, utiliser au moins une partie de cette énergie électrique ainsi générée pour assister le moteur à combustion interne de manière à fournir la puissance PD demandée, ou utiliser au moins une partie de l'énergie électrique stockée dans ladite au moins une unité de stockage d'énergie pour assister le moteur à combustion interne de manière à fournir la puissance PD demandée, ou
- g) lorsque la puissance PD demandée est supérieure à la somme de la puissance principale maximale PM développée par le moteur à combustion interne et de la puissance auxiliaire pouvant être fournie par ladite au moins une unité de stockage, ajuster le fonctionnement dudit aéronef de manière à être en mesure de fournir ladite puissance PD demandée selon l'une des étapes e) et f).
- a) collecting at least a portion of the exhaust gas when the internal combustion engine is running,
- b) supply a turbine with the energy of the gases thus collected,
- c) producing an electric current from an electric generator connected to said turbine, and
- d) comparing the maximum main power P M supplied by said internal combustion engine during the demand for power with the requested power P D ,
- e) when the maximum main power P M is at least equal to the requested power P D , storing at least a part of this electrical energy thus generated in at least one energy storage unit and / or using at least one part of this electrical energy thus generated to assist the internal combustion engine, by providing an auxiliary power P A supplementing a main power P t developed by the internal combustion engine, with P t less than P M , so that P A + P t = P D , or
- f) when the maximum main power P M is less than the power P D required for the operation of said aircraft, use at least a portion of this electrical energy thus generated to assist the internal combustion engine so as to provide the requested power P D , or using at least a portion of the electrical energy stored in said at least one energy storage unit to assist the internal combustion engine to provide the requested power P D , or
- g) when the requested power P D is greater than the sum of the maximum main power P M developed by the internal combustion engine and the auxiliary power that can be supplied by the at least one storage unit, adjust the operation of said aircraft so as to be able to provide said requested power P D according to one of the steps e) and f).
Ce procédé de gestion offre ainsi une méthode globale de gestion de la puissance demandée pour le fonctionnement d'un aéronef sans pilote notamment un drone à voilure tournante.This management method thus provides a global method for managing the power required for the operation of an unmanned aircraft, in particular a rotary wing drone.
Ce procédé de gestion d'une demande de puissance est particulièrement avantageux dans l'hypothèse où l'on souhaite augmenter la puissance installée d'un drone à décollage vertical. L'ajout de la masse liée à la mise en oeuvre de nouveaux équipements/systèmes est compensé par un gain d'efficacité globale au niveau de la chaîne de propulsion et une possibilité de récupération du drone en cas d'avarie moteur.This method of managing a power demand is particularly advantageous in the event that it is desired to increase the installed power of a vertical take-off drone. The addition of the mass related to the implementation of new equipment / systems is offset by an overall efficiency gain in the propulsion chain and a possibility of recovery of the drone in the event of engine damage.
L'augmentation de la puissance installée permet soit de transporter plus de fuel afin d'augmenter l'autonomie du drone, soit de transporter plus de charge utile, de manière plus sécurisée.The increase in installed capacity allows either to transport more fuel to increase the autonomy of the drone, or to carry more payload, more securely.
De manière avantageuse, le moteur à combustion interne étant un moteur à pistons, la turbine mise en oeuvre à l'étape b) est une turbine additionnelle ne faisant pas partie du, ou encore non reliée au, moteur à combustion interne. Cette turbine additionnelle est avantageusement placée en aval de la turbine du turbocompresseur.Advantageously, the internal combustion engine being a piston engine, the turbine used in step b) is an additional turbine that is not part of, or not connected to, the internal combustion engine. This additional turbine is advantageously placed downstream of the turbine of the turbocharger.
Ladite au moins une unité de stockage d'énergie est choisie dans le groupe comprenant une batterie électrique, un supercondensateur, ...Said at least one energy storage unit is selected from the group consisting of an electric battery, a supercapacitor, ...
Dans différents modes de réalisation particuliers de ce procédé de gestion, chacun ayant ses avantages particuliers et susceptibles de nombreuses combinaisons techniques possibles:
- à l'étape e), utilisant au moins une partie de l'énergie électrique stockée dans ladite au moins une unité de stockage d'énergie pour assister ledit moteur à combustion interne, on alimente un compresseur additionnel dudit moteur à combustion interne et/ou on alimente un moteur électrique développant une puissance auxiliaire PA.
- ledit aéronef étant un aéronef à voilure tournante, réguler l'énergie électrique stockée de sorte qu'elle soit toujours au moins égale à une énergie de récupération de l'aéronef en cas de panne dudit moteur à combustion interne.
- préalablement aux étapes e) et f), déterminer l'état de charge SOC de chaque unité de stockage d'énergie.
Lorsque l'aéronef sans pilote comporte plusieurs unités de stockage d'énergie électrique, la capacité de stockage de cet ensemble de stockage d'énergie est alors égale à la somme des capacités de stockage individuelles de, ou propres à, chaque unité de stockage.
Rappelons que l'état de charge (SOC - « State of Charge ») d'une batterie représente la quantité d'électricité (exprimée en Ah) stockée dans ladite batterie normalisée par la quantité maximale, ou capacité nominale, qui peut être stockée après une charge complète de cette batterie.
De préférence, cet aéronef étant un aéronef à voilure tournante comportant N unités de stockage d'énergie électrique, avec N > 1, on autorise la capacité d'une première unité de stockage à être inférieure ou égale à une valeur seuil Vs/N où Vs correspond à une énergie de récupération de l'aéronef en cas de panne dudit moteur à combustion interne, à l'étape f), lorsque la somme des capacités restantes dans les (N-1) autres unités de stockage est supérieure ou égale à Vs.
Bien entendu, lorsqu'une étape e) se présente, on cherchera à recharger en priorité cette unité de stockage dont la capacité est inférieure à ladite valeur seuil Vs/N de manière à ramener cette capacité à une valeur supérieure ou égale à Vs/N.
- ledit aéronef sans pilote étant un aéronef à voilure tournante comprenant au moins deux rotors, lorsque ledit moteur à combustion interne est en panne, désengager le couplage mécanique desdits rotors pour assurer une libre rotation de ces rotors et une autorotation de l'aéronef.
Ce couplage mécanique peut être un embrayage à griffes ou à friction.
De préférence, on contrôle la descente en autorotation de l'aéronef et son atterrissage lors d'une panne du moteur à combustion interne en utilisant au moins une partie de l'énergie électrique stockée dans ladite au moins une unité de stockage pour fournir audit aéronef la puissance demandée pour réaliser ce contrôle.
- ledit aéronef étant au sol, utiliser au moins une partie de l'énergie électrique stockée dans ladite au moins une unité de stockage pour fournir audit aéronef la puissance demandée, le moteur à combustion interne étant à l'arrêt,
- à l'étape e), le stockage d'au moins une partie de l'énergie électrique ainsi générée dans au moins une unité de stockage d'énergie est séquentiel ou non.
- à l'étape g), on réalise au moins une des actions suivantes : baisser l'altitude de l'aéronef, modifier la vitesse de l'aéronef.
Ces moyens de détermination de l'altitude de l'aéronef sans pilote comportent au moins un capteur barométrique permettant de mesurer les variations de pression au cours du vol, variations qui sont corrélées aux variations d'altitude.In various particular embodiments of this management method, each having its particular advantages and susceptible to many possible technical combinations:
- in step e), using at least a portion of the electrical energy stored in said at least one energy storage unit to assist said internal combustion engine, an additional compressor of said internal combustion engine and / or is supplied an electric motor developing an auxiliary power P a.
- said aircraft being a rotary wing aircraft, regulating the stored electrical energy so that it is always at least equal to a recovery energy of the aircraft in the event of failure of said internal combustion engine.
- prior to steps e) and f), determining the state of charge SOC of each energy storage unit.
When the unmanned aircraft comprises several electrical energy storage units, the storage capacity of this energy storage unit is then equal to the sum of the individual storage capacities of or specific to each storage unit.
Recall that the state of charge (SOC) of a battery represents the quantity of electricity (expressed in Ah) stored in said battery normalized by the maximum quantity, or nominal capacity, which can be stored after a full charge of this battery.
Preferably, this aircraft being a rotary wing aircraft comprising N electrical energy storage units, with N> 1, the capacity of a first storage unit is allowed to be less than or equal to a threshold value Vs / N where Vs corresponds to a recovery energy of the aircraft in the event of failure of said internal combustion engine, in step f), when the sum of the Remaining capacities in the (N-1) other storage units is greater than or equal to Vs.
Of course, when a step e) is present, it will be sought to reload this storage unit whose capacity is lower than said threshold value Vs / N in order to reduce this capacity to a value greater than or equal to Vs / N. .
- said unmanned aircraft being a rotary wing aircraft comprising at least two rotors, when said internal combustion engine is down, disengage the mechanical coupling of said rotors to ensure free rotation of these rotors and an autorotation of the aircraft.
This mechanical coupling may be a clutch clutch or friction clutch.
Preferably, the autorotation descent of the aircraft and its landing during a failure of the internal combustion engine are controlled by using at least a portion of the electrical energy stored in the at least one storage unit to supply said aircraft. the power required to perform this control.
- said aircraft being on the ground, using at least a portion of the electrical energy stored in said at least one storage unit to provide said aircraft with the requested power, the internal combustion engine being at a standstill,
- in step e), the storage of at least a portion of the electrical energy thus generated in at least one energy storage unit is sequential or not.
- in step g), at least one of the following actions is performed: lowering the altitude of the aircraft, changing the speed of the aircraft.
These means for determining the altitude of the unmanned aircraft comprise at least one barometric sensor for measuring pressure variations during flight, which variations are correlated with altitude variations.
La présente invention concerne encore un aéronef sans pilote à voilure tournante pour la mise en oeuvre du procédé de gestion d'une demande de puissance tel que décrit précédemment, ledit aéronef comportant un moteur à combustion interne suralimenté pour mettre en mouvement ladite voilure tournante, ledit moteur à combustion interne comportant un premier compresseur et fournissant une puissance principale maximale pour assurer au moins l'entrainement de ladite voilure tournante, ladite puissance principale maximale étant susceptible de varier.The present invention also relates to a rotary-wing unmanned aircraft for the implementation of the power demand management method as described above, said aircraft comprising a supercharged internal combustion engine for moving said rotary wing, said internal combustion engine having a first compressor and providing a maximum main power to ensure at least the training of said rotary wing, said maximum main power being likely to vary.
Selon l'invention, cet aéronef comprend :
- un ensemble de récupération d'énergie thermique et de transformation de cette énergie thermique en énergie électrique, cet ensemble comprenant un moyen pour collecter au moins une partie des gaz d'échappement lorsque le moteur à combustion interne fonctionne et alimenter une turbine avec lesdits gaz d'échappement ainsi collectés pour transformer l'énergie de ces gaz ainsi collectés en énergie mécanique, un générateur électrique alimenté par cette turbine pour produire une énergie électrique,
- au moins une unité de stockage d'énergie électrique configurée pour stocker au moins une partie de l'énergie électrique ainsi produite,
- un système de contrôle de la propulsion permettant de déterminer la puissance principale maximale fournie par ledit moteur à combustion interne lors d'une demande de puissance et de gérer en fonction de la puissance demandée pour au moins entraîner ladite voilure tournante, et de la puissance maximale fournie par ledit moteur à combustion interne, l'énergie électrique ainsi générée pour répondre à la demande de puissance.
- a set of thermal energy recovery and transformation of this thermal energy into electrical energy, this assembly comprising means for collecting at least a portion of the exhaust gas when the internal combustion engine is operating and supplying a turbine with said gas exhaust thus collected to transform the energy of these gases thus collected into mechanical energy, an electric generator powered by this turbine to produce electrical energy,
- at least one electrical energy storage unit configured to store at least a portion of the electrical energy thus produced,
- a propulsion control system for determining the maximum main power supplied by said internal combustion engine during a power demand and to manage as a function of the power required to at least drive said rotary wing, and power provided by said internal combustion engine, the electrical energy thus generated to meet the power demand.
Ce moteur à combustion interne suralimenté développant une puissance principale maximale PM est relié à une boîte de transmission principale pour mettre en rotation celle-ci de manière à entraîner en rotation au moins un rotor de la voilure tournante.This supercharged internal combustion engine developing a maximum main power P M is connected to a main gearbox to rotate it so as to rotate at least one rotor of the rotary wing.
Ce moteur à combustion interne est de préférence un moteur diesel.This internal combustion engine is preferably a diesel engine.
De préférence, ledit moteur à combustion interne comporte un deuxième compresseur configuré pour être alimenté en énergie électrique par ladite ou au moins une desdites unités de stockage en énergie électrique. Ce deuxième compresseur est donc un compresseur électrique.Preferably, said internal combustion engine comprises a second compressor configured to be supplied with electrical energy by said at least one of said electrical energy storage units. This second compressor is an electric compressor.
En supplément ou de manière alternative, cet aéronef comporte un moteur électrique configuré pour être alimenté en énergie électrique par ladite ou au moins une desdites unités de stockage en énergie électrique, ledit moteur électrique étant connecté à la boîte de transmission principale auquel est relié ledit moteur à combustion interne.In addition or alternatively, this aircraft comprises an electric motor configured to be supplied with electrical energy by said or at least one of said electrical energy storage units, said electric motor being connected to the main gearbox to which said engine is connected. internal combustion.
Ces éléments permettent notamment d'apporter une puissance supplémentaire pour assister le moteur à combustion interne.These elements in particular provide additional power to assist the internal combustion engine.
Avantageusement, cet aéronef à voilure tournante comprenant au moins deux rotors, il comprend un moyen pour désengager le couplage mécanique desdits rotors de manière à assurer une libre rotation de ces rotors lorsque ledit moteur à combustion interne est en panne.Advantageously, this rotary wing aircraft comprising at least two rotors, it comprises a means for disengaging the mechanical coupling of said rotors so as to ensure a free rotation of these rotors when said internal combustion engine is out of order.
De préférence, cet aéronef comporte un système de gestion de l'état de charge de chaque unité de stockage en énergie électrique pour disposer en continu d'une énergie de récupération de l'aéronef en cas de panne dudit moteur à combustion interne.Preferably, this aircraft comprises a system for managing the state of charge of each electrical energy storage unit in order to continuously dispose of a recovery energy of the aircraft in the event of failure of said internal combustion engine.
D'autres avantages, buts et caractéristiques particulières de la présente invention ressortiront de la description qui va suivre faite, dans un but explicatif et nullement limitatif, en regard des dessins annexés, dans lesquels :
- la
figure 1 est une vue schématique de l'arbre de décisions mis en oeuvre par un logiciel dans l'unité de contrôle de la propulsion (PCU) pour gérer une demande de puissance pour assurer le fonctionnement d'un drone VTOL, selon un mode de réalisation particulier de la présente invention ; - la
figure 2 est une vue très schématique d'un premier mode de réalisation d'un système de génération de puissance hybride pour un drone VTOL conforme à l'invention ; - la
figure 3 est une vue très schématique d'un deuxième mode de réalisation d'un système de génération de puissance hybride pour un drone VTOL conforme à l'invention ; - la
figure 4 est une vue très schématique d'un troisième mode de réalisation d'un système de génération de puissance hybride pour un drone VTOL conforme à l'invention ;
- the
figure 1 is a schematic view of the decision tree implemented by software in the propulsion control unit (PCU) for managing a power demand to ensure the operation of a VTOL drone, according to a particular embodiment of the present invention; - the
figure 2 is a very schematic view of a first embodiment of a hybrid power generation system for a VTOL drone according to the invention; - the
figure 3 is a very schematic view of a second embodiment of a hybrid power generation system for a VTOL drone according to the invention; - the
figure 4 is a very schematic view of a third embodiment of a hybrid power generation system for a VTOL drone according to the invention;
On notera tout d'abord que les figures ne sont pas à l'échelle.It should first be noted that the figures are not to scale.
La
Ce drone comporte une unité de stockage d'énergie dont l'alimentation en énergie électrique et la restitution sur l'arbre moteur de cette énergie électrique sont gérées par l'unité de contrôle de la propulsion (PCU).This drone comprises a power storage unit whose power supply and the return on the motor shaft of this electrical energy are managed by the propulsion control unit (PCU).
Cette stratégie pour assurer la gestion d'un appel de puissance est ici décrite sous la forme d'un arbre de décision composé de cinq (5) tests et de six (6) modes de fonctionnement.This strategy for managing a power call is here described in the form of a decision tree composed of five (5) tests and six (6) modes of operation.
Un premier test (TEST 0) évalue, au moyen de différents capteurs placés sur le moteur à combustion interne, l'état de fonctionnement de ce dernier. Si ces capteurs adressent des signaux indiquant une défaillance de celui-ci, un mode de sécurité (MODE F) est enclenché pour assurer un apport de puissance électrique directement issue de l'unité de stockage d'énergie en vue de permettre une mise en autorotation assistée et un atterrissage en douceur du drone.A first test (TEST 0) evaluates, by means of different sensors placed on the internal combustion engine, the operating state of the latter. If these sensors address signals indicating a failure thereof, a security mode (MODE F) is engaged to ensure a supply of electrical power directly from the energy storage unit to allow an autorotation assisted and a soft landing of the drone.
Le second test (TEST 1) vérifie si le moteur à combustion interne est en mesure de fournir une puissance maximale au moins égale à la puissance demandée pour satisfaire la demande :
- Si oui, le moteur à combustion interne peut, suivant un test (TEST 2) sur l'état de charge de l'unité de stockage en énergie :
- être assisté par un ensemble de récupération d'énergie thermique et de transformation de cette énergie thermique en énergie électrique, et ainsi fonctionner sous la demande de puissance pour réduire sa consommation (MODE A, SOC égale à la limite maximale), ou
- fournir l'intégralité de la puissance demandée. La puissance récupérée par l'ensemble de récupération d'énergie thermique et de transformation de cette énergie thermique en énergie électrique au niveau des gaz d'échappement est alors utilisée pour recharger l'unité de stockage d'énergie (MODE B, SOC inferieur à la limite maximale).
- Si la puissance maximale développée par le moteur au moment de la demande de puissance, est inférieure à la puissance demandée, alors :
- si la puissance totale combinée du moteur thermique à pleine charge et de l'énergie électrique issue de la récupération de l'énergie thermique au niveau des gaz d'échappement est suffisante (TEST 3), le moteur thermique est complété par cette puissance électrique générée par l'ensemble de récupération d'énergie thermique et de transformation de cette énergie thermique en énergie électrique (MODE C),
- si l'état de charge (SOC) de l'unité de stockage d'énergie est supérieur à une valeur seuil correspondant à une énergie de récupération du drone en cas de panne du moteur et si la puissance totale combinée du moteur thermique à pleine charge et celle délivrée par l'unité de stockage d'énergie est suffisante (TEST 4), le moteur thermique est complété par la puissance électrique délivré par l'unité de stockage d'énergie (MODE D),
- si le
TEST 4 échoue, le drone passe en mode de sécurité visant à réduire la demande en puissance par une modification de mission. Cette modification implique des manoeuvres (baisse de l'altitude, modification des vitesses,...) réduisant la demande de puissance (MODE E).
- If yes, the internal combustion engine can, according to a test (TEST 2) on the state of charge of the energy storage unit:
- be assisted by a set of thermal energy recovery and transformation of this thermal energy into electrical energy, and thus operate under the power demand to reduce its consumption (MODE A, SOC equal to the maximum limit), or
- provide the full power requested. The power recovered by the heat energy recovery assembly and the transformation of this thermal energy into electrical energy at the level of the exhaust gases is then used to recharge the energy storage unit (MODE B, SOC below the maximum limit).
- If the maximum power developed by the engine at the time of the power demand is less than the requested power, then:
- if the combined total power of the fully loaded engine and the electrical energy resulting from the recovery of the thermal energy at the level of the exhaust gases is sufficient (TEST 3), the engine is supplemented by this generated electrical power by the heat energy recovery assembly and transformation of this thermal energy into electrical energy (MODE C),
- if the state of charge (SOC) of the energy storage unit is greater than a threshold value corresponding to a recovery energy of the drone in the event of engine failure and if the combined total power of the engine at full load and that delivered by the energy storage unit is sufficient (TEST 4), the heat engine is completed by the electrical power delivered by the energy storage unit (MODE D),
- if
TEST 4 fails, the drone goes into safety mode to reduce the power demand by a mission change. This modification involves maneuvers (lower altitude, changing speeds, ...) reducing the power demand (MODE E).
Ce mode est provisoire et n'impose pas un atterrissage d'urgence.This mode is temporary and does not require an emergency landing.
Ce moteur à combustion interne étant un moteur à pistons, cet ensemble de récupération d'énergie thermique et de transformation de cette énergie thermique en énergie électrique comprend ici
- un moyen pour collecter au moins une partie des gaz d'échappement lorsque le moteur à combustion interne fonctionne et alimenter directement une turbine avec lesdits gaz d'échappement ainsi collectés pour transformer l'énergie résiduelle de ces gaz ainsi collectés en énergie mécanique, et
- un générateur électrique alimenté par cette turbine pour produire une énergie électrique.
- means for collecting at least a portion of the exhaust gases when the internal combustion engine is operating and supplying a turbine directly with said exhaust gases thus collected in order to transform the residual energy of these gases thus collected into mechanical energy, and
- an electric generator powered by this turbine to produce electrical energy.
Comme représenté sur les
- d'un moteur/alternateur électrique 10 fonctionnant à haut régime (vitesse de rotation d'un turbo),
- d'un moteur/alternateur électrique 11 relié à la transmission mécanique entre le bloc moteur 12 et le
rotor 13 principal, - de deux convertisseurs AC/
14, 15,DC - d'un convertisseur DC/
DC 16, - d'une unité 17 de stockage d'énergie comprenant plusieurs batteries ou supercapacités pour le stockage d'énergie électrique et son électronique de gestion permettant de surveiller l'état de charge et de santé de cette unité de stockage d'énergie électrique,
- d'une unité 18 de contrôle de la propulsion PCU (Propulsion Control Unit) permettant de gérer les flux d'énergie électrique en fonction de la demande de puissance et de l'état de charge de la batterie.
- an electric motor /
alternator 10 operating at high speed (rotational speed of a turbo), - an electric motor /
alternator 11 connected to the mechanical transmission between theengine block 12 and themain rotor 13, - two AC /
14, 15,DC converters - of a DC /
DC converter 16, - an
energy storage unit 17 comprising several batteries or supercapacities for the storage of electrical energy and its management electronics for monitoring the state of charge and health of this electrical energy storage unit, - a propulsion control unit (PCU) for
propulsion control unit 18 for managing electrical energy flows depending on the power demand and the state of charge of the battery.
Le moteur/alternateur électrique 10 fonctionnant à haut régime (vitesse de rotation d'un turbo) est capable de fournir ou de récupérer la puissance mécanique sur l'arbre du turbocompresseur du moteur 12 Diesel.The electric motor /
Le moteur/alternateur électrique 11 connecté à la transmission mécanique entre le bloc 12 moteur et le rotor 13 principal permet de fournir de la puissance mécanique aux rotors du drone VTOL.The electric motor /
Les deux convertisseurs AC/DC 14, 15 permettent de convertir la puissance électrique portée par du courant continu en puissance électrique portée par du courant alternatif et vice-versa.The two AC /
Le convertisseur DC/DC 16 permet de réguler le courant alimentant l'unité de stockage d'énergie durant la charge.The DC /
L'unité 17 de stockage d'énergie permet de stocker ou de restituer la puissance électrique vers/depuis les moteurs/alternateurs électriques.The
Claims (15)
Priority Applications (4)
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EP14307051.4A EP3034834B1 (en) | 2014-12-16 | 2014-12-16 | Method for managing power demand for the operation of an unmanned aircraft provided with an internal combustion engine |
IL243036A IL243036A0 (en) | 2014-12-16 | 2015-12-10 | Method of managing a power demand for the operation of a pilotless aircraft equipped with an internal combustion engine |
US14/966,180 US9677466B2 (en) | 2014-12-16 | 2015-12-11 | Method of managing a power demand for the operation of a pilotless aircraft equipped with an internal combustion engine |
CN201510941511.8A CN105691608B (en) | 2014-12-16 | 2015-12-16 | The method that management is equipped with the running power demand of the unmanned vehicle of internal combustion engine |
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EP14307051.4A EP3034834B1 (en) | 2014-12-16 | 2014-12-16 | Method for managing power demand for the operation of an unmanned aircraft provided with an internal combustion engine |
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EP3034834A1 true EP3034834A1 (en) | 2016-06-22 |
EP3034834B1 EP3034834B1 (en) | 2019-04-10 |
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US (1) | US9677466B2 (en) |
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Also Published As
Publication number | Publication date |
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US20160167799A1 (en) | 2016-06-16 |
CN105691608B (en) | 2019-10-18 |
EP3034834B1 (en) | 2019-04-10 |
CN105691608A (en) | 2016-06-22 |
IL243036A0 (en) | 2016-02-29 |
US9677466B2 (en) | 2017-06-13 |
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